Rocket loading and unloading tool

ABSTRACT

A tool conforms at one end to an annular nozzle end of a rocket and conforms peripherally to a tube of a launcher for the rocket so that the tool may be inserted into the tube to urge the rocket precisely into a loaded position without slipping from the nozzle and damaging elements inside the nozzle. The tool is configured to receive a blast paddle of the launcher when the paddle is pivoted across the tube to engage a detent and an igniter contact with the rocket in the loaded position. The tool is configured to urge the rocket from the loaded position for unloading from the tube and is constructed of static dissipative material.

STATEMENT OF GOVERNMENT INTEREST

The invention described herein may be manufactured and used by or forthe Government of the United States of America for government purposeswithout the payment of any royalties therefor.

BACKGROUND OF THE INVENTION

(1) Field of the Invention

The present invention relates to ordnance and, more particularly, torammers and to devices for transferring a rocket to a launcher.

(2) Description of the Related Art

A representative operating environment for the both the prior art andthe present invention is shown in FIGS. 1-5 in which various elementsare foreshortened and fragmentarily represented for illustrativeconvenience. FIGS. 2-6 show a rocket loading and unloading tool whichincorporates the principles of the present invention and is indicatedgenerally by the numeral 10. The tool, which will subsequently bedescribed in detail, includes a head 11 and a handle 12. The operatingenvironment includes a rocket 15 and a launcher 16 adapted to therocket, the rocket being depicted within an interiorly cylindricallaunching tube 17 of the launcher.

Rocket 15 has a nose end 20 and an aft end 21 and resembles a type ofmilitary rocket which has a nominal diameter of 2.75 inch (about 70 mm)diameter. Such a rocket typically has, at its aft end, features such asfolding fins which are not involved in the present invention and,accordingly, are omitted from the present application.

Such a rocket corresponding to rocket 15 is loosely and slidably fittedto a tube, which corresponds to tube 17, for loading and dischargingthrough an open forward end 22 of the tube. When loaded, the rocketextends substantially the length of the tube toward a generally open aftend 23 thereof.

Tube end 23 is associated with subsequently described devices forretaining the loaded rocket, igniting it, and subsequently releasing it.As will be described in detail, a rocket loading and unloading tool ofthe present invention is characterized by its cooperation with such arocket and such devices. However, it will be apparent to one skilled inthe ordnance art that the principles of present invention are applicableto other rocket and launcher structures and cooperative arrangementsthan those shown and described in the present application.

FIGS. 1, 2, 4, and 5 show a rocket stop 25 fixed within tube end 23 atone side thereof and protruding somewhat rearwardly therefrom. As can bevisualized from FIG. 1, when a rocket 15 is loaded into tube 17 from end22 thereof, stop 25 serves to terminate loading movement of the rocketwhen rocket end 21 engages the stop, the rocket then being in an initialloading position 26.

Transversely, stop 25 has a wing-like configuration when viewedforwardly of tube 17 from tube end 23 as in FIG. 4. This configurationserves no purpose with the depicted rocket 15, but was required for finsof other rockets to which a launcher, such as launcher 16, was adapted,this stop configuration being accommodated by the structure of tool 10in a manner subsequently described.

The portion of rocket 15 just forward of its aft end 21 has a number offeatures associated with tool 10, the depicted features being somewhatschematically represented and best shown in FIGS. 2-4. This portion ofthe rocket is constructed of steel or other substantial material andserves as a wall 30 defining a converging-diverging nozzle 31 andterminating at end 21 as annular surface 32, which circumscribes thenozzle and is the region of the rocket engaging stop 25 on loading. Athin, disk-like end shield 34 covers surface 32 and the otherwise openend of nozzle 31. This shield is, typically, constructed of aluminum andis 0.005 inch (0.127 mm) thick.

Somewhat forwardly of surface 32, rocket 15 has an electricallyconducting igniter contact band 40 extending around the rocket peripheryand electrically isolated from wall 30 by an insulating layer 41. Anigniter wire 43 extends generally centrally through the nozzle from apropulsion motor igniter, not shown, to a location axially aligned withband 40 and then turns, as shown in FIG. 3, for connection with thisband by way of an insulator extending through wall 30. A plug-likeweather seal 45, through which wire 43 extends, closes the nozzleforwardly of band 40 and is, typically, constructed of mylar material.Wall 30 has a detent engaging ring 47 which extends about the peripheryof this wall at a location forwardly of band 40. Ring 47 may be formedbetween grooves in the wall associated with fins, not shown, of therocket.

Referring to FIGS. 1 and 2, it is seen that launcher 16 has a detent andcontact mechanism 50 which is disposed at tube end 23 and extends alongtube 17 diametrically oppositely of stop 25. This mechanism includes ablast paddle 51, a rocket detent 52, and an igniter contact 53 thatcooperate with rocket 15. Since the present invention is onlyfunctionally related to mechanism 50, the internal construction thereofis not shown.

It is seen that blast paddle 51 has a pivot 55 disposed somewhat aft oftube 17 and oppositely thereof from stop 25. The paddle moves pivotallybetween a first position 56 extending parallel to the tube axis, asshown in FIG. 1, and a second position 57 shown in FIGS. 2-4 where thepaddle extends transversely across the tube, aft of a loaded rocket, andgenerally toward stop 25. The length of the paddle is such that, in thesecond position, the paddle extends across the tube for about half itsdiameter. As seen in FIG. 3, the paddle is U-shaped with its concaveside facing the tube in the second position. Mechanism 50 providespaddle 51 with an “over-center” action to retain the paddle in itsposition 56 or 57 when the paddle is moved into each of these positions,the paddle moving into its second position 57 with an audible “snap” fora purpose subsequently described.

Contact 53 and detent 52 are spaced successive distances forwardly ofstop 25 such that, axially of tube 17, they align exactly andrespectively with contact band 40 and detent ring 47 of a rocket 15 whenthe rocket is in a loaded position 60. In this position, which is shownin FIG. 2, rocket surface 32 is somewhat forward of stop 25 and paddle51 is spaced a distance axially of tube 17 from rocket surface 32.

Mechanism 50 is constructed so that, when paddle 51 is in its FIG. 1 orfirst position 56, contact 53 and detent 52 are retracted from theinterior of tube 17 so that a rocket 15 may move axially of tube 17 forloading, firing, or unloading. However, when paddle 51 is in its FIG. 2or second position 57, contact 53 and detent 52 extend into tube 17. Asa result, when a rocket is in loaded position 60 and the paddle is movedto this second position, contact 53 electrically engages band 40 forignition of the rocket motor and detent 52 engages ring 47 to hold therocket in the tube. When paddle 51 is subsequently returned to its firstposition, as by blast through nozzle 31 following motor ignition or bymanual movement of the paddle for unloading the rocket, the rocket isfreed for movement from tube 17.

It is apparent from the foregoing that, after a rocket 15 is loaded intotube 17 against stop 25 while paddle 51 is in its position 56, it isnecessary to move the rocket forwardly into its final loaded position60. To do this, paddle 51 is moved nearly into its transverse position57, and the rocket is urged forwardly from the stop until position 60 isattained; whereupon the paddle snaps into its transverse position anddetent 52 and contact 53 engage the rocket.

In the prior art, the just described movement of a rocket 15 fromengagement with stop 25 precisely into loaded position 60 was carriedout by the insertion of any convenient object, such as a dowel rod,though tube end 23 and past paddle 51 into engagement with rocket endsurface 32. A similar operation was used in unloading an unfired rocketafter moving the paddle into its first position; such an object beingused against surface 32 to urge the rocket forwardly until enough of therocket protruded from tube end 22 for grasping the rocket to withdraw itfrom the tube.

It is apparent from FIG. 2—when visualized with tool 10 of the presentinvention omitted—that, when an object such as a dowel rod is placedagainst surface 32 and forced forwardly against the rocket, the objectis likely to slip from this surface and into nozzle 31 to, at least,pierce the thin end shield 34 and, probably, destroy the electricalcontinuity of igniter wire 43. If only the shield is damaged, it can bereplaced, although not in the field. However, if the igniter continuityis broken, the entire rocket motor must be removed and disposed of.

The following four United States patents show representative prior artarrangements for positioning ordnance items in relation to generallytubular structures.

U.S. Pat. No. 311,974 issued 10 Feb. 1885 to Gatling and discloses ahand loading device having a trough which is received in a gun breechand along which a follower is motivated by a lever to correctly positiona cartridge. The face of the follower is recessed to prevent it fromtouching the primer of the cartridge.

U.S. Pat. No. 1,326,789 issued 30 Dec. 1919 to Schneider and discloses ascoop on which rests a powder charge and which has a forward edgeperipherally engaging a projectile. The scoop is inserted into a gunbore to carry the charge therein while ramming the projectile.

U.S. Pat. No. 3,120,785 issued 11 Feb. 1964 to Lorimer et al. for afolding ramming device. FIG. 2 shows a cam 31 on one rod-like guidemember disposed in a gun breech to position a pair of such members forsliding an ammunition into the gun. FIG. 8 shows the device subsequentlyrotated and bearing a “ramming bracket” 59 configured to distribute “theramming action substantially along a diameter of the ammunition tominimize tilting of the ammunition”.

U.S. Pat. No. 5,675,114 issued 7 Oct. 1997 to Thebault et al. for aloading/unloading device which carries charges into the chamber of a gunwhere a lever retains the charges. The device has an transverselyarcuate “implement” insertable entirely into the chamber, with thecharges and over this lever, for loading and unloading. The implementhas a forward end disposed to stop the device by engagement of theperiphery of a projectile forward of the charges. The implement may bemade of a conductive material “to enable the evacuation of electrostaticcharges.”

SUMMARY OF THE INVENTION

The present invention is a tool overcoming the above-identified priorart problems with rocket loading and unloading in the above-describedoperating environment.

More specifically, the tool has a generally cylindrical head which is,preferably, constructed of material which dissipates static electricity.This head conforms peripherally to the interior diameter of a rocketlauncher tube with which the tool is to function so that the head isslidably receivable in the tube and guided thereby for free movementaxially therein. The head deviates from a complete cylinder by having atleast one omitted segment so that the head has a planar surface parallelto its axis, this surface being disposed so that, when the head isreceived in the launcher tube, this surface is spaced from the tubeinterior a distance such that the head freely passes obstructions in thetube interior such as the above-described rocket stop 25.

The tool head has a forward face conforming to the aft end of a rocketwith which the tool is to function. In particular, this face has anarcuate, forwardly projecting rim conforming radially to theabove-described annular surface 32 about nozzle 31 so that, when thetool is urged against the rocket aft end, this tool face engages therocket at its surface 32 without engagement of the tool with rocket endshield 43.

As a result of the just-described structure, the tool may be insertedinto a launching tube to urge a rocket precisely into a loaded positionwithout slipping from the nozzle and damaging elements inside thenozzle.

The tool head has a rectangular slot diametrically opposite theabove-identified planar surface. This slot extends radially into thehead for a distance somewhat greater than the distance theabove-described blast paddle 51 extends across the launcher tube whenthe paddle is nearly or fully into its second position 57. Also, thewidth of this slot is somewhat greater than the width of the blastpaddle. Additionally, the axial depth of the slot is such that the toolhead does not engage the blast paddle when the paddle is disposed acrossthe launcher tube but is not fully into the second position of thepaddle corresponding to the above-described fully loaded rocket position60 where the launcher detent 52 is engaged with rocket ring 47 andlauncher igniter contact 53 is engaged with rocket contact band 40.

As a result of the structure described in the previous paragraph, a toolof the present invention is configured to receive the blast paddle ofthe launcher when the paddle is pivoted across the launcher tube justbefore and after engagement of the detent and igniter contact with therocket when the rocket is urged forwardly by the tool from the rocket'sinitial position against stop 25 into the fully loaded position 60.

Preferably, a tool of the present invention includes a rod fitted to itshead and extending axially thereof, the rod being in several sectionsand having its end opposite the head provided with a T-handle. The head,rod sections, and T-handle may be connected by screw threads forconvenient configuration of the tool for loading rockets in closequarters and for storage.

It is an object of the present invention to provide a tool formanipulating ordnance items without damage to the items.

A more specific object is provide a tool for loading or unloading arocket disposed in a launcher by application of force to an end of therocket without danger of damaging the rocket.

Another object is to provide such a tool adapted for use with a rocketdisposed in a launching tube having elements of predeterminedconfiguration for initial positioning of the rocket.

Still another object is to provide such a tool adapted for use in anoperating environment including a rocket disposed in a launching tubeassociated with elements having predetermined structures and movementsthereof for engaging the rocket to retain the rocket in the tube, toprovide ignition of the rocket, and to disengage the rocket upon firingor for unloading without firing.

An additional object is to provide such a tool which does not present astatic electricity hazard when manipulating electrically ignitedordnance items.

Yet another object is provide such a tool which facilitates the loadingand unloading of a rocket in such an operating environment and which maybe easily configured for use in a limited space and for storage.

A further object is to provide such a tool which has the foregoingadvantages, which is applicable to existing rockets and launchers, whichis economical to construct, and which is fully effective.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other objects, advantages, and novel features of the presentinvention will be apparent from the following detailed description whenconsidered with the accompanying drawings wherein:

FIG. 1 is a somewhat schematic axial section of a rocket launcher with arocket received therein, the tube and rocket being a representativeoperating environment for the present invention, and the launcherincluding a blast paddle which is depicted in a first position;

FIG. 2 is an axial section, at a scale enlarged from FIG. 1, of afterportions of the rocket and the tube together with a rocket loading andunloading tool of the present invention, the tool having a fragmentarilyrepresented handle and having a head disposed in operating relation tothe rocket, to the tube, and to retaining and igniting devicesassociated with the tube and including the blast paddle, which isdepicted in a second position;

FIG. 3 is a sectional view of the tool, launcher, and rocket taken fromthe position of line 3-3 of FIG. 2;

FIG. 4 is a sectional view of the tool, launcher, and rocket taken fromthe position of line 4-4 of FIG. 2;

FIG. 5 is a view similar to FIG. 1, but showing the tool configured andbeing used for unloading a rocket; and

FIG. 6 is a perspective view of the head of the tool.

DETAILED DESCRIPTION OF THE INVENTION

Referring to FIGS. 2 through 6, it is seen that head 11 of tool 10 maybe unitarily constructed from a cylindrical length of any suitablematerial, a static electricity static dissipative material beingpreferred so that the tool does not present an electrostatic dischargehazard when loading or unloading a rocket into tube 17. An acetylmaterial having surface and volume resistivities of 10⁹ to 10¹⁰ohms/square, as determined by ASTM Method D257, is effective for thispurpose.

As best seen in FIGS. 3 and 4, head 11 has a generally cylindricalperipheral surface 65 somewhat smaller across its greatest dimensionthan the diameter of the interior of tube 17. Head 11 thus conformsperipherally to the tube interior for slidable movement axially alongthe tube with the head and tube in generally coaxial relationship. Head11 has a planar surface 67 extending entirely along one side of the headand parallel to the axis of surface 65 so that generally cylindricalconfiguration of the head lacks a segment bounded by surface 67.Radially of the head, surface 67 is spaced from the axis of surface 65 adistance such that, when the head is received in tube 17 with surface 67facing wing-like rocket stop 25, surface 67 clears and does not engagethe stop.

As best seen from FIG. 6, it is apparent that surface 65 is an arcuateperipheral surface of head 11 and conforms to a segment of a cylinderhaving a predetermined axis, and surface 67. It is also apparent thatsurface 67 is a planar peripheral surface of the head and subtendssurface 65. It is further apparent that surface 67 extends parallel tothis axis and is disposed oppositely thereof from the center of an arcconforming to surface 65.

Head 11 has a forward face 70 conforming to the aft end of the rocket.In particular, this face has a generally central and circular recess 71so that, peripherally, the face has an arcuate rim 72 with an interiorradial dimension substantially equal to the corresponding dimension ofannular surface 32 at rocket aft end 21. The surfaces of recess 71 andrim 72, which are disposed toward rocket end 21 when head 11 is engagedtherewith, are depicted as planar and normal to the axis of surface 65.As best seen in FIG. 6, rim 72 extends radially inwardly from surface65, and recess 71 extends inwardly of head 11 in a direction along thisaxis from the rim. It is evident from FIG. 6, that face 70 is a circularsegment bounded by surfaces 65 and 67 and that surfaces 71 and 72 of theface terminate surfaces 65 and 67.

It is evident from the structure described in the preceding paragraphthat face 70 is configured to engage the rocket periphery while therocket end shield 34 is not engaged by the tool.

Head 11 defines a rectangular recess or slot 75 opposite surface 67 andextending radially into the head for a distance somewhat greater thanthe distance blast paddle 51 extends across tube 17 when the paddle isin its second position 57. Transversely of the head, the width of slot75 is somewhat greater than the width of the blast paddle as best seenin FIG. 3. As seen in FIG. 2, slot 75 extends axially into the head adistance somewhat greater than the distance the aftmost portion of thepaddle is spaced from the rocket aft end when rim 72 is pressed againstrocket surface 32 and the rocket is in its fully loaded position 60 asestablished by engagement of launcher detent 52 with ring 47 of rocket15.

From the above, it is evident that, when paddle 51 is in its transverseposition 57 and a rocket 15 is in its initial position 26, head 11 isinsertable into tube 17, without the head engaging the paddle or stop25, for urging the rocket into its final position 60 by engagement ofhead face 70 with rocket annular surface 32 without tool 10 slippingfrom the annular surface and damaging the rocker.

As seen in FIGS. 2 and 5, tool handle 12 includes a rod 80 fitted tohead 11 and extending axially thereof from an end 81 thereof oppositeface 70. The end of the rod opposite the head is, preferably, providedwith a detachable T-handle 82. The rod and handle are, typically,constructed of aluminum, and the rod may be provided in severalattachable and detachable sections 84 for convenience in storage and useof tool 10 in close quarters. For use with actual rockets of theabove-identified type of 2.75 inch nominal diameter, which have a lengthof about 6 feet (about 1800 mm), rod 75 may have two such sections about14 inches (350 mm) in length. For convenient and releasableinterconnection, head 11, T-handle 82, and each section 84 may beprovided with suitable screwthreads as indicated at head end 81 bynumeral 86.

It is evident that, as a result of the structure of head 11 whichdefines the above-described surface 67 and slot 75, tool 10 isconfigured to pass, without engaging, the obstruction in tube 17represented by stop 25 and to receive, without engaging, blast paddle 51when this paddle is pivoted across tube 17 nearly or completely intoposition 57. It will also be evident that, in loading a rocket 15 intothe tube, the structure of head 11, by virtue of surface 65 whichconforms to the tube interior, cooperates peripherally with the tubeand, by virtue of face 70 which conforms at rim 72 to rocket surface 32,cooperates axially with the rocket aft end 21 so as to prevent damage tothe rocket by the tool slipping from the rocket aft end or into nozzle31.

In such loading of a rocket 15, tool 10 is assembled by connection ofits head 11, a convenient number of the rod sections 84, and T-handle82. A blast paddle 51, which is associated with a launcher tube 17, isplaced in first position 56, and then the rocket is inserted fully intothe tube from its forward end 22 until rocket surface 32 engages stop25. The paddle is then moved substantially into its second position 57,and tool head 11 is then inserted forwardly into tube end 21. As this isdone, it is apparent that cooperation between the tube interior and theconforming head surface 65 guides the head to move substantiallycoaxially with the tube and that surface 65 is guided by tube 17 so thatthe head passes paddle 51 in its transverse position 57 and surface 67passes stop 25 so that face 70 can engage rocket end 21. As a result,further movement of the tool causes rim 72 to contact rocket surface 32without engagement of the tool head with either the stop or the blastpaddle and without danger of the tool head slipping from its peripheralengagement with surface 32 so as to damage end shield 34 or any elementof the rocket within nozzle 31. The tool is then urged forwardly, untilthe rocket moves into its fully loaded position 60 and the paddle snapsaudibly and fully into its second position 57 in which the rocket isretained by detent 47 and engaged for ignition by contact 53. Head 11 isthen withdrawn from tube 17 through tube end 23 so that the rocketremains in the loaded position engaged by the detent with end shield 34and igniter wire 43 undamaged.

Typically and as seen in FIG. 5, both rod sections 84 are utilized inunloading a rocket 15 which has not been fired. Such unloading iscarried out by returning blast paddle 51 to its first position 56 torelease the rocket from launcher tube 17 and then applying tool head 11to rocket aft end 21 and urging the rocket forwardly so that enough ofthe rocket protrudes from tube end 22 for grasping to fully withdraw therocket from the tube. As this is done, surface 65 is guided by tube 17so that the head passes paddle 51 in its extended position 56 andsurface 67 passes stop 25 so that face 70 can engage rocket end 21.

It is evident that, as in loading a rocket, the previously describedconforming relation of the head to the tube interior and to the rocketaft end, prevents damage to the rocket by the tool slipping into nozzle31. Head 11 is then withdrawn from tube 17 through tube end 23 so thatthe rocket remains in such a protruding position with end shield 34 andigniter wire 43 undamaged.

It is apparent that, in both loading and unloading a rocket 15 from atube 17 in accordance with methods of using a tool 10 of the presentinvention, the rocket is disposed in the tube; the blast paddle is inthe extended position—initially on loading and before inserting toolhead 11 into the tube on unloading; and the head is inserted into tubeend 23 with surface 65 guided by the tube so that surface 67 passesrocket stop and tool face 70 engages rocket annular surface 32 withoutslipping therefrom and affecting end shield 34 or igniter wire 43. Thetool and rocket are then urged toward tube end 22 until the rocket is ina desired position—position 60 on loading and a position protruding fromthis tube end on unloading.

Although the present invention has been herein shown and described inconnection with what is conceived as the preferred embodiment, it isrecognized that departures may be made therefrom within the scope of theinvention which is not limited to the illustrative details disclosed.

1. A tool head, comprising: an arcuate peripheral surface of the toolhead comprising a shape conforming to a segment of a cylinder with saidcylinder having a predetermined axis running a length of said cylinder;a planar peripheral surface subtending the arcuate peripheral surface,said planar peripheral surface extends perpendicular to said arcuateperipheral surface and is disposed oppositely from a center of an arc,which conforms to said arcuate peripheral surface; a forward axial endface terminating the arcuate peripheral surface and the planarperipheral surface, the forward axial end face includes at least oneplanar face surface, which extends normal to said predetermined axis;and a rectangular recess being defined by the tool head and axiallyextending into the tool head in a first direction along saidpredetermined axis from the forward axial end face, wherein saidrectangular recess radially extends openly inward from the arcuateperipheral surface into the tool head in a second directionperpendicular to said predetermined axis, wherein said rectangularrecess radially extends completely through said arcuate peripheralsurface so that said rectangular recess is oriented opposite said planarperipheral surface, and wherein the arcuate peripheral surface of thetool head extends without interruption from the planar peripheralsurface to the rectangular recess.
 2. The tool head of claim 1, furthercomprising a rod structure being disposed at an end of the tool headoppositely of said forward axial end face for attaching a handle to thetool head.
 3. The tool head of claim 1, wherein the forward axial endface comprises an arcuate outer planar face surface, which extendsradially inward from the arcuate peripheral surface, and a centralplanar face surface disposed radially within the arcuate outer planarface surface and recessed inwardly of the tool head from the arcuateouter planar face surface in a direction along said predetermined axis,and wherein said central planar face surface is substantiallyperpendicular to said arcuate outer planar face surface.
 4. The toolhead of claim 1, further comprising a screwhead releasably attaching ahandle to the tool head, said screwhead is disposed at an end of thetool head opposite of said forward axial end face.
 5. The tool head ofclaim 1, wherein the tool head is a single piece of unitaryconstruction.
 6. The tool head of claim 1, wherein the tool head isunitarily constructed of a material selected to dissipate staticelectricity.
 7. The tool head of claim 1, wherein the predetermined axisis perpendicular to the planar peripheral surface.
 8. The tool head ofclaim 1, wherein the rectangular recess is a slot shaped configuration,said slot shaped configuration comprises a width oriented transverse tosaid predetermined axis.